Hybrid exhaust heat shield for pylon mounted gas turbine engines

Abstract

The present invention is a hybrid engine exhaust heat shield assembly that includes a plurality of sections. The plurality of sections include one or more sections formed of titanium (or other high heat resistant material) by a casting process, and one or more sections formed of another heat resistant material produced in a manner other than a casting process. The plurality of sections are aerodynamically shaped for thermal protection of the aft pylon. The other heat resistant material is titanium (or other high heat resistant material) that is formed by a hot formed process, or by a super plastically-formed process. The one or more sections formed by the casting process includes heat (plume) deflector flanges.

1. A method comprising: forming one or more first parts of a first high heat resistant material by a casting process; forming one or more second parts of a second high heat resistant material using a process other than a casting process, by deforming the second high heat material into a desired aerodynamic contour; and attaching to an aircraft pylon. 
   
   
     2. The method of  claim 1 , further comprising attaching the formed parts to an aft pylon. 
   
   
     3. The method of  claim 1 , wherein the first high heat resistant material is titanium. 
   
   
     4. The method of  claim 1 , wherein the second high heat resistant material is titanium. 
   
   
     5. The method of  claim 2 , wherein deforming the second high heat material into a desired aerodynamic contour includes deforming the second high heat material using a hot forming process. 
   
   
     6. The method of  claim 2 , wherein deforming the second high heat material into a desired aerodynamic contour includes deforming the second high heat material using a super plastic forming process. 
   
   
     7. The method of  claim 1 , wherein one or more of the parts include a heat plume deflector flange. 
   
   
     8. The method of  claim 1 , wherein the parts are aerodynamically shaped. 
   
   
     9. The method of  claim 1 , wherein forming one or more second parts of a second high heat resistant material further comprises forming the one or more second parts of an austenitic nickel-chromium-iron alloy.